Details
| Original language | English |
|---|---|
| Title of host publication | ECCM 2018 - 18th European Conference on Composite Materials |
| ISBN (electronic) | 9781510896932 |
| Publication status | Published - 2018 |
| Event | 18th European Conference on Composite Materials, ECCM 2018 - Athens, Greece Duration: 24 Jun 2018 → 28 Jun 2018 |
Abstract
Simplified representations of stiffened shell structures are needed for the FE-analysis of aircraft fuselage structures on a global level. Two methods are presented to derive surrogate stiffness parameters of complex structural components. The first method is based on FE-simulations, the second uses an analytical approach. Both methods are compared to a conventional analytical approach. For the FE-based approach, the structural response to characteristic load cases of a detailed model is used to calculate beam properties. These properties are used to set up a simplified FE-model. To validate the results, the structural behavior of both models is compared. A conventional analytical approach does not respect the increased complexity of the component and leads to a mean error of 30 % compared to the validated FE-results. Therefore, a second, refined analytical approach is developed, which takes the complexity into account by discretizing the component into simple segments. From this, parameters of the entire component are derived using a spring analogy. This approach is shown to reduce the mean error to 2 %.
Keywords
- Aerospace, Aircraft fuselage design, Composite design, Omega stiffener, Simplified representation, Stiffened shell structures, Structural design
ASJC Scopus subject areas
- Materials Science(all)
- Ceramics and Composites
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ECCM 2018 - 18th European Conference on Composite Materials. 2018.
Research output: Chapter in book/report/conference proceeding › Conference contribution › Research
}
TY - GEN
T1 - Simplified representation of complex structural components for finite-element-analysis
AU - Reichert, L.
AU - Krieglsteiner, J.
AU - Schmidt, C.
AU - Horst, P.
N1 - Publisher Copyright: © CCM 2020 - 18th European Conference on Composite Materials. All rights reserved.
PY - 2018
Y1 - 2018
N2 - Simplified representations of stiffened shell structures are needed for the FE-analysis of aircraft fuselage structures on a global level. Two methods are presented to derive surrogate stiffness parameters of complex structural components. The first method is based on FE-simulations, the second uses an analytical approach. Both methods are compared to a conventional analytical approach. For the FE-based approach, the structural response to characteristic load cases of a detailed model is used to calculate beam properties. These properties are used to set up a simplified FE-model. To validate the results, the structural behavior of both models is compared. A conventional analytical approach does not respect the increased complexity of the component and leads to a mean error of 30 % compared to the validated FE-results. Therefore, a second, refined analytical approach is developed, which takes the complexity into account by discretizing the component into simple segments. From this, parameters of the entire component are derived using a spring analogy. This approach is shown to reduce the mean error to 2 %.
AB - Simplified representations of stiffened shell structures are needed for the FE-analysis of aircraft fuselage structures on a global level. Two methods are presented to derive surrogate stiffness parameters of complex structural components. The first method is based on FE-simulations, the second uses an analytical approach. Both methods are compared to a conventional analytical approach. For the FE-based approach, the structural response to characteristic load cases of a detailed model is used to calculate beam properties. These properties are used to set up a simplified FE-model. To validate the results, the structural behavior of both models is compared. A conventional analytical approach does not respect the increased complexity of the component and leads to a mean error of 30 % compared to the validated FE-results. Therefore, a second, refined analytical approach is developed, which takes the complexity into account by discretizing the component into simple segments. From this, parameters of the entire component are derived using a spring analogy. This approach is shown to reduce the mean error to 2 %.
KW - Aerospace
KW - Aircraft fuselage design
KW - Composite design
KW - Omega stiffener
KW - Simplified representation
KW - Stiffened shell structures
KW - Structural design
UR - http://www.scopus.com/inward/record.url?scp=85084164591&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85084164591
BT - ECCM 2018 - 18th European Conference on Composite Materials
T2 - 18th European Conference on Composite Materials, ECCM 2018
Y2 - 24 June 2018 through 28 June 2018
ER -